CN107162864B - A kind of hybrid motor fuel powder column and ignition charge one process of preparing - Google Patents
A kind of hybrid motor fuel powder column and ignition charge one process of preparing Download PDFInfo
- Publication number
- CN107162864B CN107162864B CN201710273182.3A CN201710273182A CN107162864B CN 107162864 B CN107162864 B CN 107162864B CN 201710273182 A CN201710273182 A CN 201710273182A CN 107162864 B CN107162864 B CN 107162864B
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- Prior art keywords
- powder column
- core model
- fuel
- mold
- propellant
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
- C06B21/0033—Shaping the mixture
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- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
Abstract
The invention discloses a kind of hybrid motor fuel powder columns and ignition charge one process of preparing；By the way that the double base propellant of extrusion forming is sleeved on the core model of cylindrical die or heart-shaped mold；Or the sheet adhering of composite propellant is bonded gap on the core model of cylindrical die or heart-shaped mold.It is connected on sleeve pedestal after core model is put on rubber washer, is poured into mold groove after the fuel prepared is melted, liquid level is less than core model and mould sleeve.For the powder column that needs solidify, is placed and solidify the regular hour under room temperature；For needing cured powder column, is placed and vacuumized in vacuum drying chamber and cure the regular hour at a certain temperature.After powder column solidifies or cures, removes mold and take out powder column, powder column both ends are trimmed to obtain required powder column.When engine ignition, double base propellant or the composite propellant burning of powder column endoporus make fuel combustion, to ensure that the pressure of engine chamber is stablized.
Description
Technical field
The invention belongs to hybrid motor technical fields, specifically, being related to a kind of hybrid motor fuel
Powder column and ignition charge one process of preparing, this method not only improves the demoulding of fuel powder column, and is conducive to fuel powder column
Reliable ignition.
Background technology
Rocket engine is the power plant of spacecraft and guided missile, with the development and progress of space technology, reliability is high,
Of low cost, the environmentally protective important directions as rocket engine development.Hybrid motor is with solid fuel and liquid
As propellant, potential application includes mainly oxidant：Sounding rocket, carrier rocket boost motor, space ship, sub- track fly
The power plant of row device, target drone, rail control engine etc..
Rocket engine is the power plant of spacecraft and guided missile, with the development and progress of space technology, reliability is high,
Of low cost, the environmentally protective important directions as its future development.Hybrid motor is with solid fuel and liquid oxidation
Agent has the following advantages as propellant：1) oxidant and fuel store respectively, therefore storage and the processing safety of engine
It is all higher；2) oxidant of propellant is mainly liquid oxygen, hydrogen peroxide, and fuel is mainly end hydroxy butadiene, paraffin, poly- second
The hydrocarbon fuels such as alkene, combustion gas is nontoxic, meets environmentally protective requirement；3) it can be realized under low cost by adjusting the flow of oxidant
The thrust of engine adjusts and multiple switching machine.
Different from solid propellant rocket, a small amount of oxidant is free of or contained only in solid-liquid rocket fuel, is burnt
Belong to diffusion combustion, the regression rate of fuel is controlled by surface thermal environment and pyrolyzing characteristic, and with the flow of oxidant,
The factors such as the characteristic size of combustion chamber pressure, chamber structure are related.In the pyrolytic process of fuel, usually fuel first melts
Liquid level is formed, after liquid level reaches pyrolysis temperature, fuel starts to be pyrolyzed.The fuel of hybrid engine be generally endoporus so as to
It is passed through oxidant, the preparation of endoporus fuel will use mold, since fuel is bonded with mold, use releasing agent, at present
Common releasing agent has vaseline, paraffin, aliphatic acid etc., these releasing agents do not allow easy firing；Since ignition charge is the one of fuel
End, and releasing agent is nonflammable, therefore the ignition delay time of fuel is increased, the comprehensive homogenous combustion of powder column cannot be made, it is unfavorable
In the trouble-free burning of fuel.
Invention content
In order to avoid the shortcomings of the prior art, a kind of hybrid motor fuel powder column of present invention proposition and igniting
Medicine one process of preparing；One layer of double base propellant or composite propellant are pasted by the endoporus in hybrid engine powder column,
When engine ignition, the double base propellant or composite propellant of powder column endoporus, which burn, makes fuel combustion, to ensure engine
The pressure of combustion chamber is stablized.
Hybrid motor fuel powder column of the present invention and ignition charge one process of preparing, it is characterised in that including with
Lower step:
Step 1. assembly mold；
(1) cylindrical die, or heart-shaped mold are selected；
(2) by the circular tube shaped double base propellant of extrusion molding or composite propellant sheet adhering on cylindrical core model；
(3) rubber washer is sleeved on threaded one end on core model, core model is threadedly coupled with mould sleeve interior base；
(4) epoxy resin, epoxy thickness 3mm are pasted on the inside of mould sleeve；
Step 2. fuel powder column is integrally prepared with ignition charge；
(1) it is 35~50% paraffin, 0.8~2% polymeric additive, 32~43%CTPB, 2.2~5% by formula
MAPO, 0~30% nanometer of Al fuel melt after pour into annular groove, liquid level of solution is less than core model and mold shell height；
(2) it places in vacuum drying chamber, temperature adjusts to 70 DEG C and pressure is evacuated to -0.09MPa；
(3) powder column is taken out after curing 7 days；
(4) powder column is removed from the molds, removes core model and powder column both ends are trimmed, obtains required powder column.
Advantageous effect
A kind of hybrid motor fuel powder column proposed by the present invention and ignition charge one process of preparing, by
The endoporus of hybrid engine powder column pastes one layer of double base propellant or composite propellant, when engine ignition, powder column endoporus
Double base propellant or composite propellant, which burn, makes fuel combustion, to ensure that the pressure of engine chamber is stablized.
(1) since the model or patch of double base propellant and composite propellant can be separated with mold well, this hair
The preparation process of bright proposition is conducive to the demoulding of fuel.
(2) since currently used releasing agent has flame retardant effect, it is unfavorable for the igniting of fuel.It is prepared using the present invention
Fuel is pasted onto the propellant at fuel endoporus when lighting a fire to powder column and burns rapidly, realizes that powder column endoporus is lighted simultaneously,
So that engine ignition is relatively reliable, ensure that combustion chamber pressure is stablized.
(3) due to being hollow inside the fuel of hybrid engine, fuel prepared by the present invention can fill up bore section vacancy,
And double base propellant and composite propellant energy are high, therefore the energy of fuel totality can be increased.
Description of the drawings
Below in conjunction with the accompanying drawings with embodiment to a kind of hybrid motor fuel powder column of the present invention and ignition charge one
Process of preparing is described in further detail.
Fig. 1 is the axial sectional view of the cylindrical die of the present invention.
Fig. 2 is the vertical view of the cylindrical die of the present invention.
Fig. 3 is the axial sectional view of the star mold of the present invention.
Fig. 4 is the vertical view of the star mold of the present invention.
Fig. 5 is fuel powder column and ignition charge one preparation flow figure.
In figure
1. 2. rubber washer of mould sleeve, 3. core model
Specific implementation mode
The present embodiment is a kind of hybrid motor fuel powder column and ignition charge one process of preparing.It will be squeezed into
The tubulose double base propellant of type is sleeved on the core model of cylindrical die or heart-shaped mold；Or the sheet adhering of composite propellant is existed
On the core model of cylindrical die or heart-shaped mold, it is bonded gap.Core model is put on into rubber washer and is threadedly attached to mold set
It on the pedestal of cylinder, is poured into mold groove after the fuel of preparation is melted, liquid level is less than core model and mould sleeve.For needing
The powder column of solidification places it under room temperature and solidifies the regular hour；For needing cured powder column, it is dry to place it in vacuum
It is vacuumized in dry case, and cures the regular hour at a certain temperature.After powder column is solidified or is cured, removes mold and take out medicine
Column trims powder column both ends with cutter, obtains required powder column.
Refering to fig. 1~Fig. 5, the present embodiment hybrid motor fuel powder column and ignition charge one process of preparing,
It is as follows:
First step assembles mold；
(1) core model of cylindrical die is selected:A diameter of 20mm, length 350mm, or the core model of heart-shaped mold are a diameter of
28mm, length 350mm, characteristic size 13mm, star angle number are 6, and star slot arc radius is 1mm, and star side angle is 90 °, star
Ascent is 0.6.Mould sleeve internal diameter is 100mm；
(2) it is 20mm by the internal diameter of extrusion molding, outer diameter 50mm, length is the tubulose double base propellant of 350mm, or long
Degree is 350mm, and width 62.8mm, thickness is the composite propellant sheet adhering of 5mm on cylindrical core model；Or it will be squeezed into
The internal diameter of shape is 28mm, outer diameter 40mm, length 350mm, and characteristic size 13mm, star angle number is 6, and star slot arc radius is
1mm, star side angle are 90 °, and the tubulose double base propellant or 6 length that star ascent is 0.6 are 350mm, width 7mm, thickness
3mm and 12 length of degree is 350mm, and the composite propellant thin slice of width 5mm, thickness 3mm are fixed on heart-shaped core model；
(3) it is 15mm core model to be had screw thread one end set top external diameter, and mould sleeve is connected to after the rubber washer that internal diameter is 3mm
Pedestal on；
(4) epoxy resin of 3mm thickness is pasted on the inside of mould sleeve.
Second step fuel powder column is integrally prepared with ignition charge；
(1) it is 35~50% paraffin, 0.8~2% polymeric additive, 32~43%CTPB, 2.2~5% by formula
MAPO, 0~30% nanometer of Al fuel melt after pour into annular groove, solution height 300mm；
(2) it is put into vacuum drying chamber, temperature adjusts to 70 DEG C and pressure is evacuated to -0.09MPa；
(3) powder column is taken out after curing 7 days；
(4) powder column is removed from the molds, removes core model, powder column both ends are trimmed with cutter；Obtain internal diameter 20~
The fuel or outer diameter of 26mm, outer diameter 100mm, length 300mm are 100mm, internal diameter 28mm, length 350mm, characteristic size
For 13mm, star angle number is 6, and star slot arc radius is 1mm, and star side angle is 90 °, the fuel that star ascent is 0.6.
Example one
In the present embodiment, the core model of cylindrical die is selected；Core model a diameter of 20mm, length 350mm, cylindrical die
Sleeve diameter is 100mm, depth 350mm.To have screw thread one end set top external diameter on the core model of cylindrical die is 15mm, internal diameter
It is 20mm, outer diameter 50mm, length by the internal diameter of extrusion molding to be connected on the pedestal of mould sleeve after the rubber washer of 3mm
Degree is that the tubulose double base propellant of 350mm is sleeved on core model.Formula is by the epoxy resin that 3mm is posted on the inside of mould sleeve
50% paraffin, 2% polymeric additive, 43%CTPB, 5%MAPO fuel melt after pour into annular groove, solution height
For 300mm；It is put into vacuum drying chamber, temperature adjusts to 70 DEG C and pressure is evacuated to -0.09MPa, and solidification takes out medicine after 7 days
Column.Powder column is removed from the molds, core model is removed, powder column both ends are trimmed with cutter；It is 20mm, outer diameter to obtain internal diameter
100mm, length are the powder column of 300mm.
Actually example two
In the present embodiment, the core model of the heart-shaped mold of selection, a diameter of 28mm, length 350mm, characteristic size 13mm,
Star angle number is 6, and star slot arc radius is 1mm, and star side angle is 90 °, and star ascent is 0.6, and heart-shaped mould sleeve internal diameter is
100mm, depth 350mm.It is 15mm by threaded one end set top external diameter of the core model of cylindrical die, Inner diameters are the rubber of 3mm
Be connected on the pedestal of mould sleeve after rubber gasket, by the internal diameter of extrusion molding be 28mm, outer diameter 40mm, length 350mm,
Characteristic size is 13mm, and star angle number is 6, and star slot arc radius is 1mm, and star side angle is 90 °, the tubulose that star ascent is 0.6
Double base propellant is sleeved on core model, and the epoxy resin of 3mm thickness is pasted on the inside of mould sleeve, will formula be 50% paraffin, it is 2% high
Molecular additives, 43%CTPB, 5%MAPO fuel melt after pour into annular groove, solution height 300mm；It is put into true
In empty drying box, temperature adjusts to 70 DEG C and pressure is evacuated to -0.09MPa, and solidification takes out powder column after 7 days.By powder column from mold
Middle taking-up, removes core model, is trimmed to powder column both ends with cutter.It is 100mm, internal diameter 28mm to obtain outer diameter, and length is
350mm, characteristic size 13mm, star angle number are 6, and star slot arc radius is 1mm, and star side angle is 90 °, and star ascent is 0.6
Powder column.
Example three
In the present embodiment, the core model of cylindrical die, a diameter of 20mm, length 350mm are selected；Cylindrical die sleeve
Internal diameter is 100mm, depth 350mm.It is 350mm by length, width 62.8mm, thickness is the composite propellant thin slice of 5mm
It is pasted onto on core model, using the gap of acetone solution junction, the core model of cylindrical die is threaded one end and covers top external diameter
For 15mm, it is connected on the pedestal of mould sleeve after the rubber washer that internal diameter is 3mm, 3mm thickness is pasted on the inside of mould sleeve
Formula is 35% paraffin, 0.8% polymeric additive, 32%CTPB, 2.2%MAPO, 30% nanometer of Al fuel by epoxy resin
It is poured into annular groove after thawing, solution height 300mm；It is put into vacuum drying chamber, temperature is adjusted to 70 DEG C and by pressure
It is evacuated to -0.09MPa, solidification takes out powder column after 7 days.Powder column is removed from the molds, core model is removed, with cutter to powder column both ends into
Row trimming；Obtain internal diameter 26mm, outer diameter 100mm, the powder column of length 300mm.
Example four
In the present embodiment, the core model of the heart-shaped mold of selection, a diameter of 28mm, length 350mm, characteristic size 13mm,
Star angle number is 6, and star slot arc radius is 1mm, and star side angle is 90 °, and star ascent is 0.6；Heart-shaped mould sleeve internal diameter is
100mm, depth 350mm.It is 350mm by 6 length, width 7mm, thickness 3mm and 12 length are 350mm, width
Composite propellant thin slice for 5mm, thickness 3mm is pasted onto on core model successively, using the gap of acetone solution junction, by cylinder
It is 15mm that the core model of shape mold, which has screw thread one end set top external diameter, and the bottom of mould sleeve is connected to after the rubber washer that internal diameter is 3mm
On seat, on the inside of mould sleeve paste 3mm thickness epoxy resin, will formula for 35% paraffin, 0.8% polymeric additive,
32%CTPB, 2.2%MAPO, 30% nanometer of Al fuel melt after pour into annular groove, solution height 300mm；It is put into
In vacuum drying chamber, temperature adjusts to 70 DEG C and pressure is evacuated to -0.09MPa, and solidification takes out powder column after 7 days.By powder column from mould
It is taken out in tool, removes core model, powder column both ends are trimmed with cutter；It is 100mm, internal diameter 28mm to obtain outer diameter, and length is
350mm, characteristic size 13mm, star angle number are 6, and star slot arc radius is 1mm, and star side angle is 90 °, and star ascent is 0.6
Powder column.
Claims (1)
1. a kind of hybrid motor fuel powder column and ignition charge one process of preparing, it is characterised in that including following step
Suddenly:
Step 1. assembly mold；
(1) cylindrical die or star mold are selected；
(2) by the circular tube shaped double base propellant of extrusion molding or composite propellant sheet adhering on cylindrical core model；
(3) rubber washer is sleeved on threaded one end on core model, core model is threadedly coupled with mould sleeve interior base；
(4) epoxy resin, epoxy thickness 3mm are pasted on the inside of mould sleeve；
Step 2. fuel powder column is integrally prepared with ignition charge；
(1) will formula be 35~50% paraffin, 0.8~2% polymeric additive, 32~43% carboxyl-terminated polybutadiene, 2.2~
5%MAPO, 0~30% nanometer of Al fuel melt after pour into annular groove, liquid level of solution is high less than core model and mold shell
Degree；
(2) it places in vacuum drying chamber, temperature adjusts to 70 DEG C and pressure is evacuated to -0.09MPa；
(3) powder column is taken out after curing 7 days；
(4) powder column is removed from the molds, removes core model and powder column both ends are trimmed, obtains required powder column.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710273182.3A CN107162864B (en) | 2017-04-25 | 2017-04-25 | A kind of hybrid motor fuel powder column and ignition charge one process of preparing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710273182.3A CN107162864B (en) | 2017-04-25 | 2017-04-25 | A kind of hybrid motor fuel powder column and ignition charge one process of preparing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107162864A CN107162864A (en) | 2017-09-15 |
| CN107162864B true CN107162864B (en) | 2018-10-16 |
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| CN201710273182.3A Expired - Fee Related CN107162864B (en) | 2017-04-25 | 2017-04-25 | A kind of hybrid motor fuel powder column and ignition charge one process of preparing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110435207B (en) * | 2019-07-31 | 2022-02-15 | 南京理工大学 | Solid fuel stamping engine fuel preparation mould |
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| CN1553135A (en) * | 2003-05-26 | 2004-12-08 | 黄振芬 | Process for filling solid rocket propellant for artillery ammunition |
| CN1651361A (en) * | 2005-03-31 | 2005-08-10 | 张根发 | Moulding product of gas producing medicinal preparation and its preparation method |
| US8465607B1 (en) * | 2008-09-18 | 2013-06-18 | The United States Of America As Represented By The Secretary Of The Navy | Higher-performance solid-rocket propellants and methods of utilizing them |
| CN203499853U (en) * | 2013-07-19 | 2014-03-26 | 晋西工业集团有限责任公司 | Rocket propellant grain fixing device |
| CN105674828A (en) * | 2016-01-21 | 2016-06-15 | 中国人民解放军军械工程学院 | Ignition destroy bomb and preparation method thereof |
| CN105840344A (en) * | 2016-04-20 | 2016-08-10 | 哈尔滨工业大学 | Preparation and safe quick demolding process for solid rocket engine inner hole burning grain |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10843979B2 (en) * | 2013-08-16 | 2020-11-24 | General Dynamics Ordnance and Tactical Systems—Canada Valleyfield Inc. | Method of manufacturing multi-layered propellant grains |
-
2017
- 2017-04-25 CN CN201710273182.3A patent/CN107162864B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1553135A (en) * | 2003-05-26 | 2004-12-08 | 黄振芬 | Process for filling solid rocket propellant for artillery ammunition |
| CN1651361A (en) * | 2005-03-31 | 2005-08-10 | 张根发 | Moulding product of gas producing medicinal preparation and its preparation method |
| US8465607B1 (en) * | 2008-09-18 | 2013-06-18 | The United States Of America As Represented By The Secretary Of The Navy | Higher-performance solid-rocket propellants and methods of utilizing them |
| CN203499853U (en) * | 2013-07-19 | 2014-03-26 | 晋西工业集团有限责任公司 | Rocket propellant grain fixing device |
| CN105674828A (en) * | 2016-01-21 | 2016-06-15 | 中国人民解放军军械工程学院 | Ignition destroy bomb and preparation method thereof |
| CN105840344A (en) * | 2016-04-20 | 2016-08-10 | 哈尔滨工业大学 | Preparation and safe quick demolding process for solid rocket engine inner hole burning grain |
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| CN107162864A (en) | 2017-09-15 |
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Granted publication date: 20181016 Termination date: 20190425 |